Method and device for determining a plurality of performance indicators relating to the flight of an aircraft, and associated computer program product

ABSTRACT

A method and device for determining a plurality of performance indicators relating to the flight of an aircraft and an associated computer program product are disclosed. In one aspect, the method includes calculating a first performance indicator based on an estimated time of arrival of the aircraft at the arrival location, an estimated flight time of the aircraft from its take-off until its arrival at the arrival location, and an estimated amount of fuel consumed by the aircraft up to the arrival location. The method further includes calculating at least one other performance indicator among second and third performance indicators. The second performance indicator is calculated based on a time difference between the estimated arrival time and the intended arrival time. The third performance indicator is calculated based on a consumption difference between the estimated amount of consumed fuel and the intended amount of consumed fuel and an additional quantity.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application claims benefit under 35 U.S.C. §119 of FrenchApplication No. 13 02433, filed Oct. 21, 2013, which is hereinincorporated by reference in its entirety.

BACKGROUND OF THE INVENTION

1. Field of the Invention

The described technology relates to a method for determining a pluralityof performance indicators relating to the flight of an aircraft to anarrival location. The method is applied by an electronic devicecomprising a memory capable of storing a flight plan of the aircraft anda predetermined value of a predicted amount of fuel consumed during theflight, the flight plan including a predicted arrival time at thearrival location.

The method comprises the calculation of a first performance indicatordepending on an estimated time of arrival of the aircraft at the arrivallocation, on an estimated flight time of the aircraft from its take-offuntil its arrival at the arrival location, and on an estimated amount offuel consumed by the aircraft up to the arrival location.

The described technology also relates to a computer program productincluding software instructions which when they are applied by acomputer, apply such a determination method.

The described technology also relates to an electronic device fordetermining the plurality of performance indicators relating to theflight of the aircraft.

2. Description of the Related Art

As used herein, an aircraft is any machine capable of flying within theearth's atmosphere, such as an airplane or further a remotely controlledaircraft, also called a drone.

In the field of flight management of the aircraft, a permanent challengeconsists of providing the pilot of the airplane, or else the operatorremotely controlling the drone, with indicators allowing optimization ofthe management of the flight according to a certain number of measuredquantities and of pre-determined constraints.

A method of the aforementioned type is known from document U.S. Pat. No.7,606,658 B2. This method consists of calculating a cost indicatordepending on the time-dependent change of the trajectory of the airplanefrom a determined point of the flight plan. This calculated indicator isthen displayed on a screen so as to be taken into account by the crew ofthe plane. The cost indicator is calculated depending on an estimationof an amount of fuel consumed by the airplane up to its finaldestination and also depending on economical parameters such as the costof the crew, the operating cost per unit time.

However, the indicator determined by such a method is not optimum, andessentially takes into account economic constraints.

SUMMARY OF CERTAIN INVENTIVE ASPECTS

An object of certain embodiments is therefore to propose a method and adevice for determining a plurality of indicators with which it ispossible to improve the relevance of the calculated indicators in orderto optimize the management of the flight of the aircraft.

For this purpose, certain embodiment disclose a method of theaforementioned type, wherein the method further comprises thecalculation of at least one other performance indicator among the secondand third performance indicators,

the second performance indicator being calculated depending on a timeshift between the estimated arrival time and the intended arrival time,and

the third performance indicator being calculated depending on aconsumption difference between the estimated amount of consumed fuel andthe intended amount of consumed fuel and on at least one additionalquantity among the following: a noise level generated by the aircraftand a duration of use of an auxiliary electric motor powered by turbinesof the aircraft.

According to other advantageous aspects of certain embodiments, thedetermination method comprises one or several of the following features,taken individually or according to all the technically possiblecombinations:

-   -   said method comprises the calculation of each of the performance        indicators among the second and third performance indicators;    -   the electronic device further comprises a display screen, and        the method further comprises the display on the screen of at        least one piece of information relating to each of the        calculated performance indicators;    -   the aircraft is an airplane including a cabin, and the method        further comprises the calculation of a fourth performance        indicator depending on the time shift and on at least one        additional quantity among the following: a cumulative duration        for the crossing of turbulence areas and a measured value of the        pressure inside the cabin;    -   said method further comprises the calculation of a global        indicator from different calculated performance indicators;    -   during the step for calculating the global indicator, each        calculated performance indicator is further multiplied by a        respective weighting coefficient and the global indicator then        verifies the following equations:

${Ind}_{G} = {\sum\limits_{i = 1}^{N}\; {\alpha_{i} \times {Ind}_{i}}}$${\sum\limits_{i = 1}^{N}\; \alpha_{i}} = 1$

wherein i is an index of the calculated performance indicator,

N represents the number of calculated performance indicators,

Ind_(G) represents the global indicator,

Ind_(i) represents the calculated performance indicator of index i, and

α_(i) represents the weighting coefficient of the calculated performanceindicator of index i.

-   -   said method further comprises the generation of an alert when at        least one performance indicator among the different calculated        performance indicators is outside a predetermined range of        values; and    -   the electronic device further comprises a display screen, and        the method comprises the determination of at least one        corrective action for improving at least one calculated        performance indicator, and the display on the screen of each        determined corrective action.

Another object of certain embodiments is a computer program productincluding software instructions which, when they are applied by acomputer, apply a method as defined above.

Another object of certain embodiments is an electronic device fordetermining a plurality of performance indicators relating to the flightof an aircraft to an arrival location,

the aircraft comprising a memory capable of storing a flight plan of theaircraft and a predetermined value of an intended amount of fuelconsumed during the flight, the flight plan including an intendedarrival time at the arrival location,

the aircraft comprising first estimation means for estimating an arrivaltime of the aircraft at the arrival location, second estimation meansfor estimating a flight time of the aircraft from its take-off until itsarrival at the arrival location, and third estimation means forestimating an amount of consumed fuel by the aircraft up to the arrivallocation,

the device comprising:

-   -   first calculation means for calculating a first performance        indicator depending on the estimated arrival time, on the        estimated flight time, and on the estimated amount of consumed        fuel,

wherein it further comprises calculation means for calculating at leastone other performance indicator among the second and third performanceindicators,

the second performance indicator being calculated depending on a timeshift between the estimated arrival time and the intended arrival time,and

the third performance indicator being calculated depending on thedifference in consumption and on at least one additional quantity amongthe group consisting in: a noise level generated by the aircraft and aduration for using an auxiliary electric motor powered by turbines ofthe aircraft.

BRIEF DESCRIPTION OF THE DRAWINGS

These features and advantages of the described technology will becomeapparent upon reading the description which follows, only given as anon-limiting example and made with reference to the appended drawings,wherein:

FIG. 1 is a schematic illustration of an aircraft comprising a flightmanagement system and a device for determining a plurality ofperformance indicators according to an embodiment,

FIG. 2 is a schematic illustration of the determination device and ofthe flight management system of FIG. 1,

FIG. 3 is a flow chart of a method for determining the plurality ofperformance indicators according to an embodiment,

FIGS. 4 to 6 illustrate function curves allowing calculation of theelementary indicators used for determining the performance indicators,

FIG. 7 is a schematic illustration of the display on a screen of thecalculated performance indicators and of a global indicator, and

FIG. 8 is a schematic illustration of the display on the screen ofdetailed pieces of information relating to a given performanceindicator.

DETAILED DESCRIPTION OF CERTAIN ILLUSTRATIVE EMBODIMENTS

In FIG. 1, an aircraft 10 is in a flight phase within the earth'satmosphere and to an arrival location, not shown. The aircraft 10comprises a management system 12 of the flight of the aircraft, alsocalled FMS (Flight Management System), an automatic pilot device 14, anelectronic device 16 for determining a plurality N of performanceindicators Ind_(i) relating to the flight of the aircraft 10.

In the exemplary embodiment of FIG. 1, the aircraft 10 is an airplaneand includes a cabin, not shown, inside which the pressure is generallydifferent from the pressure outside the aircraft 10. A crew 17, visiblein FIG. 2, and passengers, not shown, are installed inside the cabin.

In the following description, i is an indicator of the correspondingcalculated performance indicator Ind_(i), and N represents the number ofcalculated performance indicators Ind_(i).

The flight management system 12 is connected, bound to a plurality ofmeasurement units, not shown and known per se, such as an inertialreference including accelerometers and gyroscopes, a radio-altimeter, ageo-localization system. The flight management system is able todetermine the trajectory of the aircraft 10 and to estimate variousquantities, such as the altitude, the speed, from measurements carriedout with the measurement units.

The flight management system 12 includes a first processing unit 18, forexample formed with a first processor 20 and a first memory 22associated with the first processor 20.

The automatic pilot device 14 is known per se and is not described inmore detail.

The determination device 16 includes a second processing unit 24 forexample formed with a second processor 26 and a second memory 28associated with the second processor 26. Additionally, the determinationdevice 16 further includes a display screen 30, notably intended todisplay pieces of information relating to the calculated performanceindicators Ind_(i).

The first memory 22 is able to store a flight plan of the aircraft 10and a predetermined value of an intended amount of consumed fuel duringthe flight, the flight plan including an intended arrival time in thearrival location.

The first memory 22 is able to store a first software 32 for estimatingan arrival time of the aircraft in the arrival location, a secondsoftware 34 for estimating a flight time of the aircraft from its takeoff until its arrival at the arrival location, and a third software 36for estimating an amount of consumed fuel by the aircraft until thearrival location.

Alternatively, the first estimation means 32, the second estimationmeans 34 and the third estimation means 36 are made in the form ofprogrammable logic components (FPGA) or further in the form of dedicatedintegrated circuits (ASIC).

The second memory 28 is able to store a first software 38 forcalculating a first performance indicator Ind₁ of the aircraft 10depending on the estimated arrival time, on the estimated flight time,and on the estimated amount of fuel consumed.

According to the certain embodiments, the second memory 28 is furtherable to store at least one other software among a second software 40 forcalculating a second performance indicator Ind₂ of the aircraft and athird software 42 for calculating a third performance indicator Ind₃ ofthe aircraft.

The second performance indicator Ind₂ is calculated depending on a timedifference between the estimated arrival time and the intended arrivaltime.

The third performance indicator Ind₃ is calculated depending on thedifference in consumption and on an additional quantity among thefollowing: a noise level generated by the aircraft and the duration ofuse of an auxiliary electric motor, not shown, powered by turbines, notshown, of the aircraft.

Additionally, the second memory 28 is able to store a fourth software 44for calculating a fourth performance indicator Ind₄ of the aircraft.

The fourth performance indicator Ind₄ is calculated depending on thetime difference and on at least one additional quantity among thefollowing: a cumulated duration for crossing turbulence areas and ameasured value of the pressure inside the cabin.

The second memory 28 is able to store a fifth software 46 forcalculating a global indicator Ind_(G) from the different calculatedperformance indicators Ind_(i).

For calculating the global indicator Ind_(G), each performance indicatorInd_(i) is, for example, multiplied by a respective weightingcoefficient α_(i). The sum of the weighting coefficients α_(i) is equalto 1. The global indicator Ind_(G) then verifies the followingequations:

$\begin{matrix}{{Ind}_{G} = {\sum\limits_{i = 1}^{N}\; {\alpha_{i} \times {Ind}_{i}}}} & (1) \\{{\sum\limits_{i = 1}^{N}\; \alpha_{i}} = 1} & (2)\end{matrix}$

wherein Ind_(i) represents the calculated performance indicator of indexi, and

α_(i) represents the weighting coefficient of the calculated performanceindicator of index i.

The second memory 28 is able to store a software 48 for displaying onthe screen 30 at least one piece of information relating to thecalculated performance indicators Ind_(i), Ind_(G).

The second memory 28 is able to store a software 50 for determining atleast one corrective action for improving at least one calculatedperformance indicator Ind_(i), Ind_(G), each determined correctiveaction being able to be displayed on the screen 30 by the displaysoftware 48.

Additionally, the second memory 28 is able to store a software 52 forgenerating an alert when at least one performance indicator Ind_(i),Ind_(G) among the different calculated performance indicators is outsidea predetermined range of values.

Alternatively, the first calculation means 38, the second calculationmeans 48, the third calculation means 42, the fourth calculation means44, the fifth calculation means 46, the display means 48, thedetermination means 50 and the generation means 52 are made in the formof programmable logic components, or further in the form of dedicatedintegrated circuits.

The operation of the determination device 16 will now be explained bymeans of FIG. 3 illustrating a flow chart of the determination methodaccording to certain embodiments.

During an initial step 100, the flight management system 12 carries outestimations, in a way known per se, of quantities relating to the flightof the aircraft 10, such as an arrival time of the aircraft 10 at thearrival location, also noted as ETA (Estimated Time of Arrival), aflight time of the aircraft 10 from its take off until its arrival atthe arrival location, and an amount of fuel consumed by the aircraft 10up to its arrival location.

When the aircraft 10 is an airplane, the flight management system 12also estimates an arrival time of the plane 10 to the parking space,also noted as GETA (Gate Estimated Time of Arrival). The arrival timeGETA is for example equal to the sum of the arrival time ETA,corresponding to the time when the airplane 10 has landed, and of theduration for rolling between the location of the landed aircraft and theparking space.

This step for estimating the quantities relating to the flight of theaircraft is periodically carried out by the flight management system 12,notably by means of first, second and third estimation software packages32, 34, 36.

The determination device 16 then calculates, respectively during steps110, 120, 130, 140, respectively by means of its first calculationsoftware 38, of its second calculation software 40, and of its thirdcalculation software 42 and of its fourth calculation software 44, thefirst performance indicator Ind₁, the second performance indicator Ind₂,the third performance indicator Ind₃ and respectively the fourthperformance indicator Ind₄.

The steps 110, 120, 130, 140 are carried out in parallel by thedetermination device 16 from estimations of the different quantitiescarried out during step 100, without the instants for beginning each ofthese steps 110, 120, 130, 140 however being necessarily synchronized.

Each performance indicator Ind₁, Ind₂, Ind₃, Ind₄ is for examplecalculated depending on elementary indicators Ind_(i—)el_(j), wherein jis an indicator of the elementary indicator and i is an index of thecorresponding performance indicator.

Each elementary indicator Ind_(i—)el_(j) is, for example, calculatedaccording to a single quantity among the different quantities taken intoaccount for calculating the corresponding performance indicator Ind₁,Ind₂, Ind₃, Ind₄. Each performance indicator Ind₁, Ind₂, Ind₃, Ind₄ is,for example, equal to a weighted sum of these elementary indicatorsInd_(i—)el_(j).

Each elementary indicator Ind_(i—)el_(j), is, for example, expressed asa percentage. The corresponding elementary indicator Ind_(i—)el_(j) isfor example equal to 100% when the estimated value of the consideredquantity is equal to the intended value of this quantity, the indicatorbeing greater than 100% when the estimated value is better than theintended value and less than 100% when the estimated value is not asgood as the intended value. Each performance indicator Ind₁, Ind₂, Ind₃,Ind₄ is also, for example, expressed as a percentage.

The value of the elementary indicator Ind_(i—)el_(j) is, for example,expressed by a piecewise affine function of the estimated value of theconsidered quantity, as illustrated in FIG. 4. In FIG. 4, the value ofthe elementary indicator Ind_(i—)el_(j) depending on the quantity Xtaken into account is illustrated by the curve 142 which is in the formof a succession of segments. In other words, for a given interval ofvalues of the estimated quantity X relative to the intended value X₀,the value of the elementary indicator Ind_(i—)el_(j) is an affinefunction of the estimated quantity X.

In the exemplary embodiment of FIG. 4, the elementary indicatorInd_(i—)el_(j) is equal to 100% when the value of the estimated quantityX is in the range [X₀−δ₂; X₀+δ₁] around the intended value X₀, the valueof the elementary indicator Ind_(i—)el_(j) decreases linearly from 100%to 30% when the value of the estimated quantity X is greater than X₀+δ₁,the value of the elementary indicator Ind_(i) el_(j) increases linearlyfrom 100% up to 120% when the value of the estimated quantity X variesfrom X₀−δ₂ up to X₀−δ₃, and the value of the elementary indicatorInd_(i—)el_(j) is equal to 120% when the value of the estimated quantityX is less than X₀−δ₃, wherein δ₁, δ₂ and δ₃ are the differences ofvalues expressed in the same unit as a quantity with δ₂<δ₃.

During step 110, the determination device 16 calculates, by means of itsfirst calculation software 38, the first performance indicator Ind₁depending on the estimated arrival time ETA, GETA, on the estimatedflight time and on the estimated amount of consumed fuel.

The first performance indicator Ind₁ is also called a cost indicator,the estimated amount of consumed fuel allowing calculation of a fuelcost and of a carbon tax cost, the estimated flight time allowing acalculation of the maintenance cost and a cost of the crew 17, and theestimated arrival time allowing calculation of the sum of a landing tax,and optionally the sum of a noise fine and of a bonus for the crew 17.

During step 120, the determination device 16 calculates, by means of itssecond calculation software 40, the second performance indicator Ind₂depending on the time difference between the estimated arrival time andthe intended arrival time.

The value of the second performance indicator Ind₂ is, for example, apiecewise affine function of the time difference, as illustrated in FIG.5 wherein the time difference is noted as Δt and the curve 144 whichrepresents this value of the second performance indicator Ind₂ is in theform of a succession of segments. In the exemplary embodiment of FIG. 5,the second performance indicator Ind₂ has a low value, comprised between0% and 20%, while the time difference Δt relative to the intendedarrival time ETA, GETA is in absolute value greater than 15 minutes.

The second performance indicator Ind₂ is also called a time indicator,given that it directly expresses the impact of a time delta relative tothe intended arrival time.

During step 130, the determination device 16 calculates, by means of itsthird calculation software 42, the third performance indicator Ind₃depending on the consumption difference and on at least one additionalquantity among the following: a noise level generated by the aircraftand a duration of use of the auxiliary electric motor powered by theturbines of the aircraft.

The third performance indicator Ind₃ is, for example, calculateddepending on three elementary distinct indicators Ind_(3—)el₁,Ind_(3—)el₂ and Ind_(3—)el₃.

In the exemplary embodiment described, the first elementary indicatorInd_(3—)el₁ associated with the third performance indicator is onlycalculated depending on the consumption difference, the secondelementary indicator Ind_(3—)el₂ associated with the third performanceindicator is only calculated depending on the noise level generated bythe aircraft 10, and the third elementary indicator Ind_(3—)el₃associated with the third performance indicator is only calculateddepending on the duration of use of the auxiliary electric motor of theaircraft 10.

For calculating the third performance indicator Ind₃, each elementaryindicator Ind_(3—)el_(j) is, for example, multiplied by a respectiveweighting coefficient β_(j). The sum of the weighting coefficients β_(j)is equal to 1. The third performance indicator Ind₃ then verifies thefollowing equations:

$\begin{matrix}{{Ind}_{3} = {\sum\limits_{j = 1}^{J}\; {\beta_{j} \times {Ind}_{3{\_ {el}}_{j}}}}} & (3) \\{{\sum\limits_{j = 1}^{J}\; \beta_{j}} = 1} & (4)\end{matrix}$

wherein Ind_(3—)el_(j) represents the elementary indicator of index jfor the third performance indicator Ind₃, and

β_(j) represents the weighting coefficient of the elementary indicatorof index j.

The first elementary indicator value Ind_(3—)el₁ associated with thethird performance indicator is, for example, a piecewise affine functionof the amount of estimated consumed fuel, as illustrated in FIG. 6 wherethe estimated amount of consumed fuel is noted as X1 and the curve 146which represents this value of the first elementary indicatorInd_(3—)el₁ is in the form of a succession of segments.

In the exemplary embodiment of FIG. 6, the first elementary indicatorInd_(3—)el₁ has a value equal to 100% for a consumption difference ofless than 1%, relative to the intended amount of consumed fuel, noted asX1 ₀. The first elementary indicator Ind_(3—)el₁ has a value whichstrongly decreases as soon as the estimated amount of consumed fuelexceeds by more than 1% the intended amount of consumed fuel, the valueof the first elementary indicator being zero as soon as the estimatedamount of consumed fuel is greater than 108% of the intended amount ofconsumed fuel. Conversely, the first elementary indicator Ind_(3—)el₁has a value which strongly increases as soon as the estimated amount ofconsumed fuel is less than 99% of the intended amount of consumed fuel,the value of this first elementary indicator Ind_(3—)el₁ being greaterthan 120% when the estimated amount of consumed fuel is less than 97% ofthe intended amount of consumed fuel. These percentage values are givenas an example and other values may of course be considered.

The third performance indicator Ind₃ is also called an environmentalindicator, given that it expresses the impact on the environment of theconsumption difference and also of an additional quantity among thenoise level generated by the aircraft 10 and the duration of use of theauxiliary electric motor.

During step 140, the determination device 16 calculates in the case whenthe aircraft 10 is an airplane and by means of its fourth calculationsoftware 44, the fourth performance indicator Ind₄ depending on the timedifference and on at least one additional quantity from the following: acumulated duration for crossing turbulence areas and a measured value ofthe pressure inside the cabin.

The fourth performance indicator Ind₄ is also called a customersatisfaction indicator, given that it reflects the impact on thepassenger of the plane 10 of the time difference relative to theintended arrival time, is also an additional quantity among thecumulated duration for crossing turbulence areas and the measured valueof the pressure inside the cabin, which each partly characterize asensation of the quality of the flight by the passenger.

At the end of the steps 110, 120, 130, 140, the determination device 16calculates, by means of its fifth calculation software 46 and accordingto the preceding equations (1) and (2), the global index Ind_(G) fromthe different performance indicators Ind_(i) calculated from the fourperformance indicators Ind₁, Ind₂, Ind₃, Ind₄ described earlier.

The determination device 16 then displays, during step 160 and by meansof its display software 48, on the screen 30 pieces of informationrelating to the calculated performance indicators Ind_(i), asillustrated in FIG. 7. In FIG. 7, the different indicators Ind₁, Ind₂,Ind₃, Ind₄ are illustrated by an indicator in the form of a disc, theindicator being gray or hatched when the corresponding indicator Ind_(i)has not been calculated, as is the case with the fourth performanceindicator Ind₄ in the illustrated example. The indicator illustratingthe calculated performance indicator Ind_(i) is of a green color whenthe value of the corresponding indicator Ind_(i) is greater than orequal to 100%, of an orange color when the value of this indicatorInd_(i) is comprised between 80% and 100% and of red color when thevalue of this indicator Ind_(i) is less than 80%. Additionally, theindicator also contains inside the disc, a value illustrating thedifference of the value of the calculated indicator Ind_(i) relative toa reference value equal to 100%. Additionally, the values of theweighting coefficients α₁, α₂, α₃, α₄ associated with the performanceindicators Ind₁, Ind₂, Ind₃, Ind₄ are also displayed in the form of anumerical value comprised between 0 and 1. The value of the weightingcoefficient is of course zero when the corresponding indicator has notbeen calculated, such as the fourth performance indicator Ind₄ in theillustrated example. These colors are given as an example, and othercolors may of course be considered.

In FIG. 7, the global indicator Ind_(G) resulting from the calculatedperformance indicators is also displayed by means of a rectangularshaped indicator, the color of which depends on the value of the globalindicator, the color for example being green when the value of theglobal indicator Ind_(G) is greater than or equal to 100%, orange whenthe value of this indicator Ind_(G) is comprised between 80% and 100%and red when the value of this indicator Ind_(G) is less than 80%.Additionally, the indicator contains, inside the rectangle, the value ofthe global indicator Ind_(G) in the form of an integer number ofpercent.

During the next step 170, the determination device 16 then determines,by means of its determination software 50, one or several correctiveactions aiming at improving one or several calculated performanceindicators Ind_(i), and more generally aiming at improvement of theglobal indicator Ind_(G).

In order to determine the corrective action(s), the determination device16 begins by calculating the time derivatives of order 1 and 2 of theglobal indicator Ind_(G) in order to determine whether the variation ofthe global indicator Ind_(G) is a continuous variation or else if therewas a rupture in the variation of this value. In the case of continuousvariation of the value of the global indicator Ind_(G), the quantityhaving the most influence on this variation is detected notably by meansof the equations (1) to (4), the determination software 50 thendetermines one or several corrective actions aiming at limiting theinfluence of the detected quantity. In the case of rupture in thevariation of the value of the global indicator Ind_(G), the performanceindicator corresponding to this rupture is detected by means of theequations (1) and (2), and then corrective deviations are successivelyapplied to the quantities associated with the detected performanceindicator so as to determine the corrective action(s), for example, withlimitation to the three best. The proposed corrective actions are thosecorresponding to the corrective deviations improving the mostsignificantly the value of the detected performance indicator.

Additionally, during step 170, an alert is generated by thedetermination device 16 by means of its generation software 52 when atleast one performance indicator among the different calculatedperformance indicators Ind_(i) is outside a predetermined range ofvalues, and for example when the global indicator Ind_(G) is smallerthan a predetermined threshold value.

Finally, during step 180, the determined corrective action(s) aredisplayed on the screen 30 by the determination device 16 by means ofits display software 48, as illustrated in FIG. 8.

FIG. 8 illustrates the display of more detailed information relating toa selected performance indicator among the different performanceindicators Ind₁, Ind₂, Ind₃, Ind₄. These pieces of information areaccessible by choosing a tab 162 corresponding to the desiredperformance indicator, such as for example the first performanceindicator Ind₁ in the example of FIG. 8.

The presented detailed pieces of information for example comprise afirst line 164 of information relating to the intended values of thedifferent quantities taken into account for calculating thecorresponding performance indicator Ind_(i), a second line 166 ofinformation relating to the present values of the different quantitiesand a third line 168 of information relating to alternative values ofthese different quantities according to a determined corrective actionby means of the determination software 50. In the example of FIG. 8,three quantities, i.e. the estimated amount of consumed fuel X1, and twoother quantities X2, X3, are taken into account for calculating thefirst performance indicator Ind₂. For displaying the second and thirdlines 166, 168, hatched areas correspond to already elapsed values ofthe respective quantities X1, X2, and the non-hatched areas correspondto the estimated remaining values of these quantities, the elapsedvalues being noted as X1 _(—) e, X2 _(—) e and the estimated remainingvalues being noted as X1 _(—) r, X2 _(—) r.

It is thus conceivable that the determination method and device 16according to certain embodiments allows improvement in the relevance ofthe calculated indicators Ind_(i) in order to optimize flight managementof the aircraft 10.

One skilled in the art will understand that the weighting used forcalculating the global indicator Ind_(G) and each weighting used forcalculating a respective performance indicator Ind_(i) are each aweighting with a weighted sum, or a variable weighting, or further aweighting depending on several variables.

In other words, in the case of the weighted sum, each weightingcoefficient α_(i), β_(j) is constant and the sum of the weightingcoefficients α_(i), β_(j) is equal to 1, in accordance with theequations (2) and (4) notably.

In the case of variable weighting, each weighting coefficient α_(i),β_(j) is of variable value, while having a sum of weighting coefficientsalways equal to 1.

In the case of weighting depending on several variables x, y, z, eachweighting coefficient is of a variable value and depends on one orseveral of these variables x, y, z.

The value of each weighting coefficient is positive, zero or negative.When the value of a weighting coefficient is negative, the indicatorassociated with said weighting coefficient is then removed from theother indicators.

By dependency on one or several variables x, y, z, is notably meantdependency depending on the result of an equation or of an inequationinvolving said variable(s) x, y, z.

As a purely illustrative example, the weighting coefficient α₁ of thecalculated performance indicator of index 1 depends on the variables xand y, the weighting coefficient α₂ of the performance indicator ofindex 2 depends on the variable x, the weighting coefficient α₃ of theperformance indicator of index 3 depends on the variable y and theweighting coefficient α₄ of the calculated performance indicator ofindex 4 depends on the variables x and z. The coefficient α₁ for exampleassumes a first value when the variable x is less than the variable y,and a second value when the variable x is greater than or equal to thevariable y. The coefficient α₄ for example is negative when the variablex is equal to twice of the variable z.

The variables x, y, z for example are performance indicators orelementary indicators being subject to the weighting. Alternatively, thevariables x, y, z are distinct from the indicators subject to weighting.

In the case of weighting depending on several variables x, y, z, thefunction allowing calculation of the global indicator Ind_(G) and/oreach respective performance indicator Ind_(i) is also generally aso-called multi-criteria function.

The computing environment included in the flight management system 12and/or the determination device 16 includes computer programs or code.Computer programs are executed by data processors. Each program maycontain a number of modules and whether modularized or not, instructionsto be read and executed by a computing environment. Instructions referto computer-implemented steps for processing information in the system.Instructions can be implemented in software, firmware or hardware andinclude any type of programmed step undertaken by components of thesystem.

The computing environment also includes one or more memories such as thefirst memory 22 and the second memory 28. Memory refers to electroniccircuitry that allows information, typically computer data, to be storedand retrieved. Memory can refer to external devices or systems, forexample, disk drives or tape drives. Memory can also refer to fastsemiconductor storage (chips), for example, random access memory (RAM)or various forms of read only memory (ROM) are directly connected to theprocessor. Other types of memory include flash, RRAM, STTRAM, DRAM,SRAM, hard disk drives, etc. Such computer readable memories aregenerally non-transitory.

As can be appreciated by one of ordinary skill in the art, each of themodules or software of the program(s) can include various sub-routines,procedures, definitional statements, and macros. Each of the modules aretypically separately compiled and linked into a single executableprogram. Therefore, any description of modules or software is used forconvenience to describe the functionality of the system. Thus, theprocesses that are undergone by each of the modules may be arbitrarilyredistributed to one of the other modules, combined together in a singlemodule, or made available in a shareable dynamic link library. Furthereach of the modules could be implemented in hardware.

A person of skill in the art would readily recognize that steps ofvarious above-described methods can be performed by programmedcomputers. Herein, some embodiments are also intended to cover programstorage devices, e.g., digital data storage media, which are machine orcomputer readable and encode machine-executable or computer-executableprograms of instructions, wherein said instructions perform some or allof the steps of said above-described methods. The program storagedevices may be, e.g., digital memories, magnetic storage media such as amagnetic disks and magnetic tapes, hard drives, or optically readabledigital data storage media. The embodiments are also intended to covercomputers programmed to perform said steps of the above-describedmethods.

While there have been shown and described and pointed out thefundamental novel features of the invention as applied to certaininventive embodiments, it will be understood that the foregoing isconsidered as illustrative only of the principles of the invention andnot intended to be exhaustive or to limit the invention to the preciseforms disclosed. Obvious modifications or variations are possible inlight of the above teachings. The embodiments discussed were chosen anddescribed to provide the best illustration of the principles of theinvention and its practical application to enable one of ordinary skillin the art to utilize the invention in various embodiments and withvarious modifications as are suited to the particular use contemplate.All such modifications and variations are within the scope of theinvention as determined by the appended claims when interpreted inaccordance with the breadth to which they are entitled.

What is claimed is:
 1. A method for determining a plurality ofperformance indicators relating to the flight of an aircraft to anarrival location, the method being applied by an electronic device, theaircraft comprising a memory configured to store a flight plan of theaircraft and a predetermined value of an intended amount of consumedfuel during the flight, the flight plan including an intended arrivaltime at the arrival location, the method comprising: calculating a firstperformance indicator based on: i) an estimated time of arrival of theaircraft at the arrival location, ii) an estimated flight time of theaircraft from its take-off until its arrival at the arrival location,and iii) an estimated amount of fuel consumed by the aircraft up to thearrival location; and calculating at least one other performanceindicator among second and third performance indicators, wherein thesecond performance indicator is calculated based on a time differencebetween the estimated arrival time and the intended arrival time, andwherein the third performance indicator is calculated based on: i) aconsumption difference between the estimated amount of consumed fuel andthe intended amount of consumed fuel and ii) at least one additionalquantity among the following: a noise level generated by the aircraftand a duration of use of an auxiliary electric motor powered by turbinesof the aircraft.
 2. The method according to claim 1, further comprisingcalculating both of the second and third performance indicators.
 3. Themethod according to claim 1, wherein the electronic device furthercomprises a display screen and wherein the method further comprisesdisplaying on the display screen at least one piece of informationrelating to each of the calculated performance indicators.
 4. The methodaccording to claim 1, wherein the aircraft is an airplane including acabin and wherein the method further comprises calculating a fourthperformance indicator based on: i) the time difference and ii) at leastone additional quantity among the following: a cumulated duration forcrossing turbulence areas and a measured value of the pressure insidethe cabin.
 5. The method according to claim 1, wherein the methodfurther comprises calculating a global indicator from the differentcalculated performance indicators.
 6. The method according to claim 5,wherein calculating the global indicator comprises multiplying eachcalculated performance indicator by a respective weighting coefficient,the global indicator satisfying the following equations: $\begin{matrix}{{Ind}_{G} = {\sum\limits_{i = 1}^{N}\; {\alpha_{i} \times {Ind}_{i}}}} \\{{\sum\limits_{i = 1}^{N}\; \alpha_{i}} = 1}\end{matrix}$ wherein i is an index of a calculated performanceindicator, N represents the number of calculated performance indicators,Ind_(G) represents the global indicator, Ind_(i) represents thecalculated performance indicator of index i, and α_(i) represents theweighting coefficient of the calculated performance indicator of indexi.
 7. The method according to claim 1, wherein the method furthercomprises generating an alert when at least one performance indicatoramong the different calculated performance indicators is outside apredetermined range of values.
 8. The method according to claim 1,wherein the electronic device further comprises a display screen andwherein the method further comprises: determining at least onecorrective action for improving at least one calculated performanceindicator; and displaying on the display screen each determinedcorrective action.
 9. A computer program product including softwareinstructions which when executed by a computer, cause the computer toperform a method comprising: calculating a first performance indicatorbased on: i) an estimated time of arrival of an aircraft at an arrivallocation, ii) an estimated flight time of the aircraft from its take-offuntil its arrival at the arrival location, and iii) an estimated amountof fuel consumed by the aircraft up to the arrival location; andcalculating at least one other performance indicator among second andthird performance indicators, wherein the second performance indicatoris calculated based on a time difference between the estimated arrivaltime and an intended arrival time, and wherein the third performanceindicator is calculated based on: i) a consumption difference betweenthe estimated amount of consumed fuel and an intended amount of consumedfuel and ii) at least one additional quantity among the following: anoise level generated by the aircraft and a duration of use of anauxiliary electric motor powered by turbines of the aircraft.
 10. Anelectronic device for determining a plurality of performance indicatorsrelating to the flight of an aircraft to an arrival location, theaircraft comprising a memory configured to store a flight plan of theaircraft and a predetermined value of an intended amount of fuelconsumed during the flight, the flight plan including an intendedarrival time at the arrival location, the aircraft further comprising:i) a first estimation module configured to estimate an arrival time ofthe aircraft at the arrival location, ii) a second estimation moduleconfigured to estimate a flight time of the aircraft from its take-offto its arrival at the arrival location, and iii) a third estimationmodule configured to estimate an amount of fuel consumed by the aircraftright up to the arrival location, the device comprising: a firstcalculation module configured to calculate a first performance indicatorbased on: i) the estimated arrival time, ii) the estimated flight timeand iii) the estimated consumed fuel amount; and a second calculationmodule configured to calculate at least one other performance indicatoramong second and third performance indicators, wherein the secondperformance indicator is calculated based on a time difference betweenthe estimated arrival time and the intended arrival time, and whereinthe third performance indicator is calculated based on: i) theconsumption difference and ii) at least one additional quantity amongthe following: a noise level generated by the aircraft and a duration ofuse of an auxiliary electric motor powered by turbines of the aircraft.11. The electronic device of claim 10, wherein at least one of theperformance indicators is calculated based on a plurality of elementaryindicators and a plurality of weighting coefficients respectivelycorresponding to the elementary indicators.
 12. The electronic device ofclaim 11, wherein each elementary indicator is defined as a piecewiseaffine function of an estimated value of a considered flight variable.